Individual aircraft life monitoring is required to ensure safety and economy of aircraft structure, and fatigue damage evaluation based on collected operational data of aircraft is an integral part of it.
A critical safety issue for the design of aircraft structure is vulnerability and damage tolerance due to foreign object impact.
Despite lightning strikes, traditional aluminium planes are usually able to continue their journey safely – the high electrical conductivity of aluminium can dissipate the electricity through the aircraft structure quickly without causing any damage.
The rapid repair of battle damage to composite aircraft structure has been investigated by Defence Science and Technology Organisation and Cooperative Research Centre for Advanced Composite Structures, Australia.
These results should be useful in evaluation in the damage tolerance evaluation of aircraft structures with multi-site damage.
Safety cuts (or confidence cuts) are used in the repair of fatigue damaged fastener holes in aircraft structure to ensure that any residual crack is removed in the repair process.
It was nothing less than the first modern aircraft structure.
"Any engineer acquainted with basic aircraft structure..
This paper proposes a comprehensive seven-stage life prediction model for the reliability analysis of aging aircraft structures under multiple site damage (MSD) due to corrosion fatigue.
In order to reduce the costs related to corrosion damage in aircraft structures, it is vital to develop new robust, accurate and reliable damage detection methods.
